Accession Number:

AD0425765

Title:

AN AERODYNAMIC STUDY OF A 1/6-SCALE ISOLATED INLET FOR THE F-111 AIRPLANE, IN THE RESEARCH AND DEVELOPMENT FACILITY, FOR GENERAL DYNAMICS/ FT. WORTH,

Descriptive Note:

Corporate Author:

GENERAL DYNAMICS DAINGERFIELD TEX ORDNANCE AEROPHYSICS LAB

Personal Author(s):

Report Date:

1963-11-27

Pagination or Media Count:

3.0

Abstract:

Aerodynamic tests were conducted on a 16-scale isolated inlet for the F-111 airplane. A total of 97 inlet configurations were tested. The 16-scale model included an inlet with the cross section equivalent to a segment of a circle of 90 degrees and 20 minutes. The model was equipped with a variable position spike and an exit throttle plug for back pressure regulation. The inlet was tested in a Mach 2.04 free-jet stream with free-stream total pressure and temperature of 25 psia and 150 F. Variations of spike, cowl, and side plate designs were tested. These incorporated various methods of boundary layer bleed for the purpose of retarding unstable inlet conditions and helping obtain higher total pressure recoveries. The maximum total pressure recovery recorded during these tests was 0.92 however, pressure recoveries as high as 0.90 were not uncommon. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE